WO2011118474A1 - Seal structure for turbine rotor - Google Patents

Seal structure for turbine rotor Download PDF

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Publication number
WO2011118474A1
WO2011118474A1 PCT/JP2011/056216 JP2011056216W WO2011118474A1 WO 2011118474 A1 WO2011118474 A1 WO 2011118474A1 JP 2011056216 W JP2011056216 W JP 2011056216W WO 2011118474 A1 WO2011118474 A1 WO 2011118474A1
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WO
WIPO (PCT)
Prior art keywords
turbine rotor
turbine
seal structure
thermal expansion
protrusion
Prior art date
Application number
PCT/JP2011/056216
Other languages
French (fr)
Japanese (ja)
Inventor
吉彦 武藤
良造 田中
Original Assignee
川崎重工業株式会社
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
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Publication date
Application filed by 川崎重工業株式会社 filed Critical 川崎重工業株式会社
Priority to EP11759280.8A priority Critical patent/EP2551492B1/en
Priority to US13/636,982 priority patent/US9359958B2/en
Priority to CA 2793966 priority patent/CA2793966C/en
Publication of WO2011118474A1 publication Critical patent/WO2011118474A1/en

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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/28—Arrangement of seals
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
    • F01D11/025—Seal clearance control; Floating assembly; Adaptation means to differential thermal dilatations
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/50—Intrinsic material properties or characteristics
    • F05D2300/502—Thermal properties
    • F05D2300/5021—Expansivity
    • F05D2300/50212—Expansivity dissimilar

Definitions

  • the present invention relates to a seal structure for a gas turbine device, and more particularly to a seal structure for sealing between members inside a gas turbine engine, particularly between members around a turbine rotor.
  • a gas turbine burns combustion air and fuel compressed by a compressor in a combustor, expands the generated high-temperature and high-pressure combustion gas in the turbine, and extracts the output to the outside.
  • it is preferable that all of the generated combustion gas is supplied to the turbine.
  • a connecting portion between the annular members constituting the interior of the gas turbine engine for example, a gap between a support member of a turbine blade that is a rotating member and a support member of a turbine stationary blade that is a fixed member.
  • some of the high-temperature combustion gas from the combustor may leak radially inward. When the amount of combustion gas leakage is large, the performance of the gas turbine engine deteriorates.
  • Patent Document 1 needs to be provided with a multi-stage winding path (tortuous) path) in order to ensure the sealing performance of the turbine rotor, which greatly affects the performance of the gas turbine engine.
  • Directional dimensions increase.
  • the seal member is greatly deformed due to a slight difference in thermal expansion between members to be sealed or a difference in centrifugal force, and the seal member is easily damaged by repeating this.
  • An object of the present invention is to provide a sealing structure for a turbine rotor in a gas turbine that has a structure and can reliably seal the turbine rotor over a long period of time.
  • the turbine rotor seal structure according to the present invention is a turbine rotor seal structure in a gas turbine engine.
  • the seal structure includes a protrusion provided on the turbine rotor, an outer member disposed radially outside the protrusion, and supported so as to be displaceable in the radial direction, and disposed radially inside the protrusion.
  • a labyrinth seal formed with an inner member supported so as to be displaceable in a direction is included, and the thermal expansion coefficient of the inner member is set to be larger than the thermal expansion coefficient of the outer member.
  • the difference between the coefficient of thermal expansion of the inner member and that of the outer member is preferably in the range of 2 ⁇ 10 ⁇ 6 to 6 ⁇ 10 ⁇ 6 / ° C.
  • the radial outer portion of the labyrinth seal is sealed by the projection of the turbine rotor that is displaced radially outward by thermal expansion and centrifugal force, and the outer member having low thermal expansion.
  • the sealability of the radially inner portion of the labyrinth seal is greatly improved by the projections of the turbine rotor and the inner member that thermally expands greatly. Therefore, the sealing performance of the seal structure is improved without increasing the axial dimension of the labyrinth seal.
  • An abradable material may be provided in a portion of the outer member facing the protruding portion, and an abradable material may be provided in a portion of the inner member facing the protruding portion.
  • the turbine rotor can be reliably sealed over a long period of time because it has a structure that can follow the radial expansion of the turbine rotor without increasing the axial dimension. This improves the performance and reliability of the gas turbine engine.
  • FIG. 2 It is a fragmentary sectional view explaining the gas turbine engine which employ
  • A) is the cross-sectional view seen from the II direction in FIG. 2, and is a figure explaining the connection state by the 1st connection member and the 2nd connection member.
  • B) is a cross-sectional view as seen from the direction II-II in FIG. 2, showing a state of connection by a third connection member. It is sectional drawing in the III-III line
  • gas turbine 1 compresses introduced air 100 from the outside with a compressor 3 and leads it to a combustor 5.
  • the injected fuel 200 is mixed with the introduced air 100 and burned, and the turbine 7 is driven by the high-temperature and high-pressure combustion gas 250 obtained.
  • an axial flow type compressor 3 is used.
  • a large number of moving blades 13 are arranged on the outer peripheral surface of a front / rear divided compressor rotor 11 ⁇ / b> A constituting the front portion of the rotating portion of the gas turbine 1.
  • the introduced air 100 introduced from the intake cylinder 19 is compressed.
  • a diffuser 23 formed by the housing 15 and a diffuser inner peripheral wall 21 provided on the radially inner side thereof is provided. The compressed air 120 is fed toward the combustor 5 through the diffuser 23.
  • a plurality of combustors 5 are arranged at equal intervals along the circumferential direction of the gas turbine 1.
  • the combustor 5 mixes and combusts the compressed air 120 fed from the compressor 3 and the fuel 200 injected into the combustor 5.
  • the generated high-temperature and high-pressure combustion gas 250 flows from the turbine nozzle (first stage stationary blade) 25 into the turbine 7.
  • the turbine 7 includes a high-pressure turbine rotor 11B and a low-pressure turbine rotor 11C that constitute the rear part of the rotating portion of the gas turbine 1, and a turbine casing 27 that covers the rotors 11B and 11C.
  • the high-pressure turbine rotor 11B is connected to the compressor rotor 11A so as to rotate integrally, and drives the compressor rotor 11A.
  • the high pressure turbine rotor 11B and the low pressure turbine rotor 11C are not connected.
  • a plurality of stages of turbine stationary blades 29 are attached to the inner peripheral portion of the turbine casing 27 at a predetermined interval.
  • the high pressure turbine rotor 11B and the low pressure turbine rotor 11C are provided downstream of the turbine stationary blades 29 of each stage.
  • a plurality of stages of turbine blades 31 are provided so as to be positioned.
  • the entire rotors 11A, 11B, and 11C are rotatably supported via bearing devices 35, 37, and 39 disposed in the front, center, and rear of the housing 15.
  • the central bearing device 37 is covered with a bearing housing 49, and a bearing housing space 51 is formed between the compressor rotor 11 ⁇ / b> A and the bearing housing 49.
  • the bearing housing 49 is connected to the downstream end of the diffuser inner peripheral wall 21 of the diffuser 23 by a bolt (not shown), and is formed by the outer side of the bearing housing 49 and the outer wall of the combustor 5 that are located downstream of the diffuser 23. This space forms a compressed air transfer space 55 that guides the compressed air 120 from the diffuser 23 to the combustor 5.
  • an adapter ring 57 is connected between the turbine side (rear side) end portion 49 a of the bearing housing 49 and a connecting flange portion 25 a protruding from the inner diameter side of the turbine nozzle 25.
  • the members 59, the second connecting member 61, and the third connecting member 63 are connected to each other.
  • the adapter ring 57 is formed as a two-membered annular member composed of an outer member 67 positioned on the radially outer side and an inner member 69 positioned on the radially inner side, which are connected to each other.
  • the side end portion 67 a and the outer peripheral side end portion 69 a of the inner member 69 are connected via the second connecting member 61.
  • the outer peripheral portion of the adapter ring 57 that is, the outer peripheral side end portion 67 b of the outer member 67 is connected to a connecting flange portion 25 a protruding from the inner diameter side of the turbine nozzle 25 by a third connecting member 63.
  • the bearing housing 49, the outer member 67 of the adapter ring 57, the inner member 69, and the turbine nozzle 25 are relatively immovable in the circumferential direction and relatively moved in the radial direction by the first to third connecting members 59, 61, 63. It is connected and supported.
  • Such a support has a first connecting member 59 having a pin portion 59a and a screw portion 59b, a pin portion 61a and a mounting portion 61b in a radially extending insertion groove provided in the inner member 69 and the turbine nozzle 25.
  • the second connecting member 61 and the third connecting member 63 having the pin portion 63a and the screw portion 63b are inserted through the second connecting member 61 and the third connecting member 63, respectively.
  • this connection structure will be described in detail.
  • the first connecting member 59 is inserted through the annular first restricting member 70A, and a threaded portion 59b provided at the base end thereof is screwed into the first restricting member 70A.
  • the pin portion 59a on the distal end side of the first connecting member 59 is formed as a cylindrical pin and has a circular cross section.
  • the inner peripheral side end 69 b of the inner member 69 has an inner dimension in the circumferential direction that matches the outer diameter dimension of the first connecting member 59 and an inner diameter in the radial direction that is larger than the outer diameter dimension of the first connecting member 59.
  • An engaging portion 69ba made of a groove having a size is provided.
  • the inner member 69 By inserting and engaging the first connecting member 59 with the engaging portion 69ba of the inner member 69, the inner member 69 is relatively immovable relative to the bearing housing 49 in the circumferential direction and relatively movable in the radial direction. Connected. The inner member 69 is also movable in the axial direction with respect to the bearing housing 49, and its axial position is regulated by the first regulating member 70A shown in FIG. 2 and the boss 49b of the bearing housing.
  • the first regulating member 70A is fixed to the bearing housing 49 by a bolt B1 disposed at a circumferential position different from that of the first connecting member 59. Specifically, as shown in FIG. 4, the first restricting member 70A is fixed to the bearing housing 49 by a bolt B1 screwed into the boss 49b of the bearing housing 49, and the first restricting member 70A causes the FIG.
  • the second connecting member 61 is a pin member that does not have a head portion and a screw portion, and an attachment portion 61 b provided at one end portion thereof is inserted into the inner peripheral side end portion 67 a of the outer member 67 and is fixed by welding 300. ing.
  • the pin part 61a of the 2nd connection member 61 is formed as a double-sided pin which has plane part 61aa and 61aa which regulate the circumferential direction position on both sides of the circumferential direction.
  • the outer end 69a of the inner member 69 has an inner dimension in the circumferential direction that matches the outer dimension between the plane portions 61aa and 61aa and an inner dimension in the radial direction that is larger than the outer dimension in the radial direction of the pin portion 61a.
  • An engaging portion 69aa made of a groove is provided.
  • An annular second restricting member 70B is fixed to the front surface of the inner peripheral end 67a of the outer member 67 shown in FIG. 2 by a bolt B2 disposed at a circumferential position different from that of the second connecting member 61. Yes. Specifically, as shown in FIG. 4, the second restricting member 70B is inserted into the boss 70Ba of the second restricting member 70B and is screwed into the inner peripheral side end 67a of the outer member 67 by the bolt B2. 67 is fixed. The front surface of the second connecting member 61 shown in FIG. 2 is covered with the second restricting member 70B.
  • the inner member 69 is also movable in the axial direction with respect to the outer member 67, and the axial position thereof is restricted by the second restricting member 70 ⁇ / b> B and the outer peripheral end 67 a of the outer member 67.
  • the third connecting member 63 is formed as a threaded pin having a threaded portion 63b provided at the proximal end near the head 63c.
  • the outer peripheral side end 67b of the outer member 67 has an annular connecting recess that opens radially outward.
  • the threaded portion 63b of the third connecting member 63 is screwed into the front wall 67ba, and the rear wall 67bb is engaged.
  • the distal end portion of the pin portion 63a on the distal end side of the third connecting member 63 is fitted in the provided fitting hole 67d. As shown in FIG.
  • the coupling flange portion 25a of the turbine nozzle 25 is provided with an engagement portion 25aa having the same structure as the engagement portion 69ba on the inner peripheral side of the inner member 69.
  • the engaging portion 25aa of the nozzle 25 engages with the pin portion 63a of the third connecting member 63, the outer member 67 cannot move relative to the turbine nozzle 25 in the circumferential direction and can move relative to the radial direction. It is connected.
  • the connecting members 59, 61, 63 and the engaging portions 69aa, 69ba, 25aa are provided at equal intervals in three or more locations in the circumferential direction. Further, as shown in FIG. 2, when the gas turbine engine 1 is assembled, the adapter ring 57 is interposed between the outer peripheral end 67 b of the outer member 67 and the base 25 b of the connecting flange 25 a of the turbine nozzle 25. A gap 71 for absorbing radial expansion is provided. Further, a sealing member 73 that seals between the outer flange 67 and the outer member 67 is provided on the connecting flange portion 25 a of the turbine nozzle 25.
  • the turbine rotor blade 31 is formed on the outer peripheral portion of the rotor disk 75 that forms the high-pressure turbine rotor 11B.
  • a pre-swirl for extracting a part of the compressed air 120 as cooling air 125 from the compressed air transfer space 55 to the inner diameter side space 77 between the inner member 69 and the rotor disk 75.
  • a nozzle 79 is provided in the inside of the inner member 69 of the adapter ring 57.
  • a cooling passage 81 for introducing the cooling air 125 into the rotor disk 75 is provided in a portion of the rotor disk 75 facing the pre-swivel nozzle 79.
  • the cooling air 125 led out from the compressed air transfer space 55 to the inner diameter side space 77 cools the outside and the inside of the rotor disk 75.
  • the outer diameter side space 83 formed between the outer member 67 of the adapter ring 57 and the rotor disk 75 the first stage turbine rotor blade 31 as a rotating member and the turbine nozzle 25 as a non-rotating member are provided. A part of the high-temperature combustion gas G passing through the combustion gas passage 84 of the turbine 7 flows in as leak gas 260 from the gap 33.
  • annular recess 85 that is recessed forward is provided on the rear side of the connecting portion between the outer member 67 and the inner member 69 of the adapter ring 57.
  • annular protrusion 87 that protrudes in the axial direction of the high-pressure turbine rotor 11 ⁇ / b> B and extends in the circumferential direction is provided at a radial position corresponding to the recess 85 on the front side of the rotor disk 75.
  • a plurality of labyrinth teeth 89 are respectively formed on the radially outer side and the inner side.
  • a seal structure is formed. With this sealing structure, the space between the outer diameter side space 83 into which the high-temperature leaking gas 260 flows and the inner diameter side space 77 into which the cooling air 125 flows is sealed. As a result, it is possible to prevent the leakage gas 260 in the outer diameter side space 83 from entering the inner diameter side space 77 and reducing the cooling action.
  • an abradable material 95 having a honeycomb structure made of a nickel-iron alloy is fixed to portions of the outer member 67 and the inner member 69 facing the labyrinth teeth 89 of the protrusion 87.
  • the wear of the protrusion 87, the outer member 67, and the inner member 69 forming the seal structure SS, which is a labyrinth seal mechanism, is suppressed, and the life of the seal structure is improved.
  • the inner member 69 of the adapter ring 57 is made of a material having a larger coefficient of thermal expansion than the outer member 67.
  • the difference in coefficient of thermal expansion between the inner member 69 and the outer member 67 is preferably in the range of 2 ⁇ 10 ⁇ 6 to 6 ⁇ 10 ⁇ 6 / ° C., and is 3 ⁇ 10 ⁇ 6 to 5 ⁇ 10 ⁇ 6 / ° C. More preferably, it is in the range.
  • stainless steel such as SUS321 is used as a material for forming the inner member 69
  • a Ni-based heat-resistant alloy such as WASPALOY (registered trademark) is used as a material for forming the outer member 67.
  • the thermal expansion coefficient of SUS321 is about 18 ⁇ 10 ⁇ 6 / ° C.
  • the thermal expansion coefficient of WASPALOY is about 14 ⁇ 10 ⁇ 6 / ° C.
  • the difference between the two is about 4 ⁇ 10 ⁇ 6 / ° C.
  • the inner member 69 of the adapter ring 57 is formed of a material having a larger coefficient of thermal expansion than the outer member 67, so that the sealing performance of the seal structure is improved. That is, when the gas turbine engine 1 is operated, the protrusion 87 is displaced radially outward as the turbine rotor (high-pressure turbine rotor 11B) expands radially outward due to thermal expansion and centrifugal force. Is less displaced radially outward due to thermal expansion. Therefore, the sealing performance of the outer labyrinth seal 91 having a sealing structure is ensured by the radially outer portion of the protrusion 87 and the outer member 67 having a low coefficient of thermal expansion.
  • the inner member 69 having a large coefficient of thermal expansion largely displaces radially outward due to thermal expansion, thereby following the displacement of the protrusion 87, so that the sealing performance of the inner labyrinth seal 93 of the seal structure is greatly improved. .
  • the sealing performance of the seal structure can be improved without increasing the axial dimension of the entire seal structure.
  • four labyrinth teeth 89 are provided on each of the radially outer side and the inner side of the protrusion 87, and therefore, the same axis as when four labyrinth teeth 89 are provided only on the radially outer side. While maintaining the directional dimension, the sealing performance is equivalent to the case where eight labyrinth teeth 89 are provided only on the radially outer side.
  • the number of labyrinth teeth 89 provided on the radially outer side and the inner side of the protrusion 87 can be selected as appropriate.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

Provided is a seal structure for a turbine rotor in a gas turbine, which can follow the expansion of the turbine rotor in the radial direction without increasing the dimension in the axial direction and which can reliably seal the turbine rotor for a long period of time. The seal structure contains labyrinth seals (91, 93) constituted by a projection (87) provided on a turbine rotor (11B), an external member (67) which is disposed on the outside in the radial direction of the projection (87) and which is supported so as to move in the radial direction, and an internal member (67) which is disposed on the inside in the radial direction of the projection (87) and which is supported so as to move in the radial direction. The coefficient of thermal expansion of the internal member (69) is set so as to be larger than the coefficient of thermal expansion of the external member (67).

Description

タービンロータのシール構造Turbine rotor seal structure
　本発明は、ガスタービン装置のシール構造に係り、ガスタービンエンジン内部の部材間、特にタービンロータ周辺の部材間をシールするシール構造に関する。 The present invention relates to a seal structure for a gas turbine device, and more particularly to a seal structure for sealing between members inside a gas turbine engine, particularly between members around a turbine rotor.
　ガスタービンは、圧縮機で圧縮された燃焼用空気と燃料を燃焼器で燃焼させ、発生する高温・高圧の燃焼ガスをタービン中で膨張させることにより外部に出力を取り出し、発電機、プロペラ、車両、機械の駆動などに用いられる。燃焼ガスが高温・高圧であるほど高出力が得られる。ガスタービンエンジンにおいて高出力を得るには、生成された燃焼ガスはその全てがタービンに供給されることが好ましい。しかしながら、実際には、ガスタービンエンジンの内部を構成する環状の部材間の連結部分、例えば、回転部材であるタービン動翼の支持部材と固定部材であるタービン静翼の支持部材との隙間を介して、燃焼器からの高温の燃焼ガスの一部が径方向内側に漏れることがある。燃焼ガスの漏れ量が多いと、ガスタービンエンジンの性能が低下する。 A gas turbine burns combustion air and fuel compressed by a compressor in a combustor, expands the generated high-temperature and high-pressure combustion gas in the turbine, and extracts the output to the outside. Generator, propeller, vehicle Used for machine driving. The higher the combustion gas is, the higher the output is. In order to obtain high output in a gas turbine engine, it is preferable that all of the generated combustion gas is supplied to the turbine. In practice, however, a connecting portion between the annular members constituting the interior of the gas turbine engine, for example, a gap between a support member of a turbine blade that is a rotating member and a support member of a turbine stationary blade that is a fixed member. Thus, some of the high-temperature combustion gas from the combustor may leak radially inward. When the amount of combustion gas leakage is large, the performance of the gas turbine engine deteriorates.
　このような漏れガスを抑えるために、例えば、タービンロータの周囲をシールするラビリンスシール部材を、径方向に移動可能なように、撓み部材によって支持する構造が提案されている。このシール構造によれば、遠心力及び熱膨張でタービンロータが径方向に伸縮し、シール部分が径方向に変位した場合であっても、ラビリンスシール部材がシール部分の変位に追随してシール性が確保される（例えば、特許文献１参照。）。 In order to suppress such leakage gas, for example, a structure in which a labyrinth seal member that seals the periphery of the turbine rotor is supported by a bending member so as to be movable in the radial direction has been proposed. According to this seal structure, even when the turbine rotor expands and contracts in the radial direction due to centrifugal force and thermal expansion, and the seal portion is displaced in the radial direction, the labyrinth seal member follows the displacement of the seal portion and seals. Is ensured (see, for example, Patent Document 1).
特開平８－２７７７０１号公報JP-A-8-277701
　特許文献１に開示されたシール構造は、ガスタービンエンジンの性能に大きな影響を与えるタービンロータのシール性を確保するため、曲がりくねった通路（tortuous path）を多段に設ける必要があり、ラビリンスシールの軸方向寸法が増大する。この場合、シールする部材間のわずかな熱膨張の差や遠心力の差によって、シール部材が大きく変形し、これが繰り返されることによりシール部材が破損し易くなるという問題があった。 The seal structure disclosed in Patent Document 1 needs to be provided with a multi-stage winding path (tortuous） path) in order to ensure the sealing performance of the turbine rotor, which greatly affects the performance of the gas turbine engine. Directional dimensions increase. In this case, there is a problem that the seal member is greatly deformed due to a slight difference in thermal expansion between members to be sealed or a difference in centrifugal force, and the seal member is easily damaged by repeating this.
　したがって、本発明はこのような問題点を解決することを課題としてなされたものであり、その目的とするところは、軸方向寸法の増大を伴うことなくタービンロータの径方向の膨張に追随可能な構造を有し、長期にわたって確実にタービンロータをシールできるガスタービンにおけるタービンロータのシール構造を提供することにある。 Therefore, the present invention has been made to solve such problems, and the object of the present invention is to follow the radial expansion of the turbine rotor without increasing the axial dimension. An object of the present invention is to provide a sealing structure for a turbine rotor in a gas turbine that has a structure and can reliably seal the turbine rotor over a long period of time.
　本発明に係るタービンロータのシール構造は、ガスタービンエンジンにおけるタービンロータのシール構造である。このシール構造は、タービンロータに設けられた突起部と、この突起部の径方向外側に配置され、径方向に変位可能に支持された外側部材と、突起部の径方向内側に配置され、径方向に変位可能に支持された内側部材とで形成されるラビリンスシールを含み、内側部材の熱膨張率が、外側部材の熱膨張率よりも大きく設定されている。内側部材の熱膨張率と外側部材の熱膨張率との差は、２×１０－６～６×１０－６／℃の範囲内にあることが好ましい。 The turbine rotor seal structure according to the present invention is a turbine rotor seal structure in a gas turbine engine. The seal structure includes a protrusion provided on the turbine rotor, an outer member disposed radially outside the protrusion, and supported so as to be displaceable in the radial direction, and disposed radially inside the protrusion. A labyrinth seal formed with an inner member supported so as to be displaceable in a direction is included, and the thermal expansion coefficient of the inner member is set to be larger than the thermal expansion coefficient of the outer member. The difference between the coefficient of thermal expansion of the inner member and that of the outer member is preferably in the range of 2 × 10 −6 to 6 × 10 −6 / ° C.
　この構成によれば、ガスタービンエンジンの運転時に、熱膨張および遠心力により径方向外側に変位するタービンロータの突起部と、熱膨張の小さい外側部材とによって、ラビリンスシールの径方向外側部分のシール性が確保されるとともに、上記タービンロータの突起部と、大きく熱膨張する内側部材とによって、ラビリンスシールの径方向内側部分のシール性が大幅に向上する。したがって、ラビリンスシールの軸方向寸法の増大をともなうことなく、当該シール構造のシール性が向上する。 According to this configuration, when the gas turbine engine is operated, the radial outer portion of the labyrinth seal is sealed by the projection of the turbine rotor that is displaced radially outward by thermal expansion and centrifugal force, and the outer member having low thermal expansion. As a result, the sealability of the radially inner portion of the labyrinth seal is greatly improved by the projections of the turbine rotor and the inner member that thermally expands greatly. Therefore, the sealing performance of the seal structure is improved without increasing the axial dimension of the labyrinth seal.
　外側部材における突起部と対向する部分には、アブレイダブル材が設けられていてもよく、また、内側部材における突起部と対向する部分にアブレイダブル材が設けられていてもよい。この構成によれば、ラビリンスシールを形成する突起部と外側部材、内側部材との摩耗が抑制され、ラビリンスシールの寿命が向上する。 An abradable material may be provided in a portion of the outer member facing the protruding portion, and an abradable material may be provided in a portion of the inner member facing the protruding portion. According to this configuration, wear between the protrusions forming the labyrinth seal, the outer member, and the inner member is suppressed, and the life of the labyrinth seal is improved.
　本発明によれば、軸方向寸法の増大を伴うことなくタービンロータの径方向の膨張に追随可能な構造を有するので、長期にわたって確実にタービンロータをシールできる。これにより、ガスタービンエンジンの性能及び信頼性が向上する。 According to the present invention, the turbine rotor can be reliably sealed over a long period of time because it has a structure that can follow the radial expansion of the turbine rotor without increasing the axial dimension. This improves the performance and reliability of the gas turbine engine.
本発明の実施の形態に係るタービンロータのシール構造を採用したガスタービンエンジンを説明する部分断面図である。It is a fragmentary sectional view explaining the gas turbine engine which employ | adopted the seal structure of the turbine rotor which concerns on embodiment of this invention. 本発明の実施の形態に係るタービンロータのシール構造を説明する縦断面図である。It is a longitudinal section explaining the seal structure of the turbine rotor concerning an embodiment of the invention. （ａ）は、図２におけるＩ－Ｉ方向から見た横断面図であり、第１連結部材及び第２連結部材による連結状態を説明する図である。（ｂ）は、図２におけるII－II方向から見た横断面図であり、第３連結部材による連結状態を示す図である。(A) is the cross-sectional view seen from the II direction in FIG. 2, and is a figure explaining the connection state by the 1st connection member and the 2nd connection member. (B) is a cross-sectional view as seen from the direction II-II in FIG. 2, showing a state of connection by a third connection member. 図３（ａ）のIII－III線における断面図である。It is sectional drawing in the III-III line | wire of Fig.3 (a).
　　１　ガスタービンエンジン
　　３　圧縮機
　　５　燃焼器
　　７　タービン
　　１１Ｂ　高圧タービンロータ（タービンロータ）
　　５７　アダプタリング
　　６７　外側部材
　　６９　内側部材
　　８７　突起部
　　８９　ラビリンス歯
　　９１　外側ラビリンスシール
　　９３　内側ラビリンスシール
　　１００　導入空気
　　１２０　圧縮空気
　　１２５　冷却空気
　　２００　燃料
　　２５０　燃焼ガス
　　２６０　漏れガス DESCRIPTION OF SYMBOLS 1 Gas turbine engine 3 Compressor 5 Combustor 7 Turbine 11B High-pressure turbine rotor (turbine rotor)
57 Adapter ring 67 Outer member 69 Inner member 87 Protruding part 89 Labyrinth tooth 91 Outer labyrinth seal 93 Inner labyrinth seal 100 Inlet air 120 Compressed air 125 Cooling air 200 Fuel 250 Combustion gas 260 Leakage gas
　以下、本発明の実施の形態に係るタービンロータのシール構造について、添付図面に従って説明する。なお、以下の説明では、方向や位置を表す用語（例えば、「前側」、「後側」等）を便宜上用いるが、これらは、発明の理解を容易にするためであり、それらの用語によって本発明の技術的範囲が限定的に解釈されるべきではない。以下の説明においては、ガスタービン１の圧縮機側を「前側」、タービン側を「後側」と称する。 Hereinafter, a seal structure of a turbine rotor according to an embodiment of the present invention will be described with reference to the accompanying drawings. In the following description, terms indicating the direction and position (for example, “front side”, “rear side”, etc.) are used for convenience, but these are for facilitating understanding of the invention. The technical scope of the invention should not be limitedly interpreted. In the following description, the compressor side of the gas turbine 1 is referred to as “front side”, and the turbine side is referred to as “rear side”.
　図１に示すように、ガスタービンエンジン１（以下、「ガスタービン１」と称する。）は、外部からの導入空気１００を圧縮機３で圧縮して燃焼器５に導き、燃焼器５内に噴射された燃料２００を導入空気１００と混合して燃焼させ、得られた高温高圧の燃焼ガス２５０によりタービン７を駆動する。 As shown in FIG. 1, a gas turbine engine 1 (hereinafter referred to as “gas turbine 1”) compresses introduced air 100 from the outside with a compressor 3 and leads it to a combustor 5. The injected fuel 200 is mixed with the introduced air 100 and burned, and the turbine 7 is driven by the high-temperature and high-pressure combustion gas 250 obtained.
　本実施形態では、軸流型の圧縮機３を用いている。この軸流型圧縮機３は、ガスタービン１の回転部分の前部を構成する前後２分割型の圧縮機ロータ１１Ａの外周面に、多数の動翼１３が配置されており、これら動翼１３と、ハウジング１５の内周面に多数配置された静翼１７との組み合わせにより、吸気筒１９から導入した導入空気１００を圧縮する。圧縮機３の下流側には、ハウジング１５と、その径方向内側に設けられたディフューザ内周壁２１とによって形成されたディフューザ２３が設けられている。圧縮空気１２０は、ディフューザ２３を介して燃焼器５に向けて送給される。 In this embodiment, an axial flow type compressor 3 is used. In this axial flow type compressor 3, a large number of moving blades 13 are arranged on the outer peripheral surface of a front / rear divided compressor rotor 11 </ b> A constituting the front portion of the rotating portion of the gas turbine 1. In combination with a large number of stationary blades 17 arranged on the inner peripheral surface of the housing 15, the introduced air 100 introduced from the intake cylinder 19 is compressed. On the downstream side of the compressor 3, a diffuser 23 formed by the housing 15 and a diffuser inner peripheral wall 21 provided on the radially inner side thereof is provided. The compressed air 120 is fed toward the combustor 5 through the diffuser 23.
　燃焼器５は、ガスタービン１の周方向に沿って複数個が等間隔に配置されている。燃焼器５は、圧縮機３から送給された圧縮空気１２０と、燃焼器５内に噴射された燃料２００とを混合して燃焼する。そして、生成された高温高圧の燃焼ガス２５０がタービンノズル（第１段静翼）２５からタービン７内に流入する。 A plurality of combustors 5 are arranged at equal intervals along the circumferential direction of the gas turbine 1. The combustor 5 mixes and combusts the compressed air 120 fed from the compressor 3 and the fuel 200 injected into the combustor 5. The generated high-temperature and high-pressure combustion gas 250 flows from the turbine nozzle (first stage stationary blade) 25 into the turbine 7.
　タービン７は、ガスタービン１の回転部分の後部を構成する高圧タービンロータ１１Ｂ及び低圧タービンロータ１１Ｃと、これらロータ１１Ｂ，１１Ｃを覆うタービンケーシング２７とを備えている。高圧タービンロータ１１Ｂは圧縮機ロータ１１Ａに一体回転するように連結され、圧縮機ロータ１１Ａを駆動する。高圧タービンロータ１１Ｂと低圧タービンロータ１１Ｃは連結されていない。タービンケーシング２７の内周部には複数段のタービン静翼２９が所定間隔をおいて取り付けられ、一方、高圧タービンロータ１１Ｂ及び低圧タービンロータ１１Ｃには、各段のタービン静翼２９の下流側に位置するように複数段のタービン動翼３１が設けられている。 The turbine 7 includes a high-pressure turbine rotor 11B and a low-pressure turbine rotor 11C that constitute the rear part of the rotating portion of the gas turbine 1, and a turbine casing 27 that covers the rotors 11B and 11C. The high-pressure turbine rotor 11B is connected to the compressor rotor 11A so as to rotate integrally, and drives the compressor rotor 11A. The high pressure turbine rotor 11B and the low pressure turbine rotor 11C are not connected. A plurality of stages of turbine stationary blades 29 are attached to the inner peripheral portion of the turbine casing 27 at a predetermined interval. On the other hand, the high pressure turbine rotor 11B and the low pressure turbine rotor 11C are provided downstream of the turbine stationary blades 29 of each stage. A plurality of stages of turbine blades 31 are provided so as to be positioned.
　ロータ１１Ａ，１１Ｂ，１１Ｃの全体は、ハウジング１５内の前部、中央部、後部に配置された軸受装置３５，３７，３９を介して回転自在に支持されている。中央部軸受装置３７は、軸受ハウジング４９によって覆われており、圧縮機ロータ１１Ａと軸受ハウジング４９との間が軸受収容空間５１を形成している。軸受ハウジング４９は、ディフューザ２３のディフューザ内周壁２１の下流端部に、図示しないボルトにより連結されており、ディフューザ２３の下流に位置する、軸受ハウジング４９の外側と燃焼器５の外壁とで形成される空間が、ディフューザ２３から燃焼器５へと圧縮空気１２０を導く圧縮空気移送空間５５を形成している。 The entire rotors 11A, 11B, and 11C are rotatably supported via bearing devices 35, 37, and 39 disposed in the front, center, and rear of the housing 15. The central bearing device 37 is covered with a bearing housing 49, and a bearing housing space 51 is formed between the compressor rotor 11 </ b> A and the bearing housing 49. The bearing housing 49 is connected to the downstream end of the diffuser inner peripheral wall 21 of the diffuser 23 by a bolt (not shown), and is formed by the outer side of the bearing housing 49 and the outer wall of the combustor 5 that are located downstream of the diffuser 23. This space forms a compressed air transfer space 55 that guides the compressed air 120 from the diffuser 23 to the combustor 5.
　図２に示すように、軸受ハウジング４９のタービン側（後側）端部４９ａと、タービンノズル２５の内径側に突設された連結フランジ部２５ａとの間には、アダプタリング５７が第１連結部材５９、第２の連結部材６１及び第３の連結部材６３を介して連結されている。アダプタリング５７は、互いに連結された、径方向外側に位置する外側部材６７と径方向内側に位置する内側部材６９とからなる２つ割りの環状部材として形成されており、外側部材６７の内周側端部６７ａと内側部材６９の外周側端部６９ａとが第２連結部材６１を介して連結されている。アダプタリング５７の外周部、つまり外側部材６７の外周側端部６７ｂは、タービンノズル２５の内径側に突設された連結フランジ部２５ａに、第３連結部材６３により連結されている。 As shown in FIG. 2, an adapter ring 57 is connected between the turbine side (rear side) end portion 49 a of the bearing housing 49 and a connecting flange portion 25 a protruding from the inner diameter side of the turbine nozzle 25. The members 59, the second connecting member 61, and the third connecting member 63 are connected to each other. The adapter ring 57 is formed as a two-membered annular member composed of an outer member 67 positioned on the radially outer side and an inner member 69 positioned on the radially inner side, which are connected to each other. The side end portion 67 a and the outer peripheral side end portion 69 a of the inner member 69 are connected via the second connecting member 61. The outer peripheral portion of the adapter ring 57, that is, the outer peripheral side end portion 67 b of the outer member 67 is connected to a connecting flange portion 25 a protruding from the inner diameter side of the turbine nozzle 25 by a third connecting member 63.
　軸受ハウジング４９、アダプタリング５７の外側部材６７、内側部材６９、およびタービンノズル２５は、第１～第３連結部材５９，６１，６３により、周方向に相対移動不能に、且つ径方向に相対移動可能に連結されて支持されている。このような支持は、内側部材６９及びタービンノズル２５に設けられた径方向に延びる挿通溝に、ピン部５９ａ及びねじ部５９ｂを有する第１連結部材５９と、ピン部６１ａ及び取付け部６１ｂを有する第２連結部材６１と、ピン部６３ａ及びねじ部６３ｂを有する第３連結部材６３とを、それぞれ挿通することによりなされる。以下、この連結構造について詳細に説明する。 The bearing housing 49, the outer member 67 of the adapter ring 57, the inner member 69, and the turbine nozzle 25 are relatively immovable in the circumferential direction and relatively moved in the radial direction by the first to third connecting members 59, 61, 63. It is connected and supported. Such a support has a first connecting member 59 having a pin portion 59a and a screw portion 59b, a pin portion 61a and a mounting portion 61b in a radially extending insertion groove provided in the inner member 69 and the turbine nozzle 25. The second connecting member 61 and the third connecting member 63 having the pin portion 63a and the screw portion 63b are inserted through the second connecting member 61 and the third connecting member 63, respectively. Hereinafter, this connection structure will be described in detail.
　図２に示すように、第１連結部材５９は環状の第１規制部材７０Ａに挿通され、その基端部に設けられたねじ部５９ｂが第１規制部材７０Ａに螺合している。図３（ａ）に示すように、第１連結部材５９の先端側のピン部５９ａは、円柱状のピンとして形成されており、円形状の断面を有している。他方、内側部材６９の内周側端部６９ｂには、第１連結部材５９の外径寸法に合致する周方向の内寸及び、第１連結部材５９の外径寸法よりも大きい径方向の内寸を有する溝からなる係合部６９ｂａが設けられている。第１連結部材５９を内側部材６９の係合部６９ｂａに挿通して係合させることにより、内側部材６９が軸受ハウジング４９に対して周方向に相対移動不能に、且つ径方向に相対移動可能に連結される。内側部材６９は、軸受ハウジング４９に対して軸方向にも移動可能であり、その軸方向位置は、図２で示した第１規制部材７０Ａと、軸受ハウジングのボス４９ｂとにより規制されている。 As shown in FIG. 2, the first connecting member 59 is inserted through the annular first restricting member 70A, and a threaded portion 59b provided at the base end thereof is screwed into the first restricting member 70A. As shown in FIG. 3A, the pin portion 59a on the distal end side of the first connecting member 59 is formed as a cylindrical pin and has a circular cross section. On the other hand, the inner peripheral side end 69 b of the inner member 69 has an inner dimension in the circumferential direction that matches the outer diameter dimension of the first connecting member 59 and an inner diameter in the radial direction that is larger than the outer diameter dimension of the first connecting member 59. An engaging portion 69ba made of a groove having a size is provided. By inserting and engaging the first connecting member 59 with the engaging portion 69ba of the inner member 69, the inner member 69 is relatively immovable relative to the bearing housing 49 in the circumferential direction and relatively movable in the radial direction. Connected. The inner member 69 is also movable in the axial direction with respect to the bearing housing 49, and its axial position is regulated by the first regulating member 70A shown in FIG. 2 and the boss 49b of the bearing housing.
　第１規制部材７０Ａは、第１連結部材５９と異なる周方向位置に配設されたボルトＢ１により軸受ハウジング４９に固定されている。具体的には、図４に示すように、軸受ハウジング４９のボス４９ｂに螺合したボルトＢ１によって第１規制部材７０Ａが軸受ハウジング４９に固定されており、この第１規制部材７０Ａによって、図２で示した内側部材６９の内周側の係合部６９ｂａの前面が覆われている。 The first regulating member 70A is fixed to the bearing housing 49 by a bolt B1 disposed at a circumferential position different from that of the first connecting member 59. Specifically, as shown in FIG. 4, the first restricting member 70A is fixed to the bearing housing 49 by a bolt B1 screwed into the boss 49b of the bearing housing 49, and the first restricting member 70A causes the FIG. The front surface of the engaging portion 69ba on the inner peripheral side of the inner member 69 shown in FIG.
　第２連結部材６１は、頭部及びねじ部を有しないピン部材であり、その一端部に設けられた取付け部６１ｂが外側部材６７の内周側端部６７ａに挿通され、溶接３００により固定されている。図３（ａ）に示すように、第２連結部材６１のピン部６１ａは、周方向の両側に周方向位置を規制する平面部６１ａａ，６１ａａを有する二面ピンとして形成されている。内側部材６９の外周側端部６９ａには、これら平面部６１ａａ，６１ａａ間の外寸に合致する周方向の内寸及び、ピン部６１ａの径方向の外寸よりも大きい径方向の内寸を有する溝からなる係合部６９ａａが設けられている。この係合部６９ａａに第２連結部材６１を挿通して係合させることにより、内側部材６９が外側部材６７に対して周方向に相対移動不能に、且つ径方向に相対移動可能に連結される。 The second connecting member 61 is a pin member that does not have a head portion and a screw portion, and an attachment portion 61 b provided at one end portion thereof is inserted into the inner peripheral side end portion 67 a of the outer member 67 and is fixed by welding 300. ing. As shown to Fig.3 (a), the pin part 61a of the 2nd connection member 61 is formed as a double-sided pin which has plane part 61aa and 61aa which regulate the circumferential direction position on both sides of the circumferential direction. The outer end 69a of the inner member 69 has an inner dimension in the circumferential direction that matches the outer dimension between the plane portions 61aa and 61aa and an inner dimension in the radial direction that is larger than the outer dimension in the radial direction of the pin portion 61a. An engaging portion 69aa made of a groove is provided. By inserting and engaging the second connecting member 61 into the engaging portion 69aa, the inner member 69 is connected to the outer member 67 so as not to be relatively movable in the circumferential direction and relatively movable in the radial direction. .
　図２に示した外側部材６７の内周側端部６７ａの前面には、環状の第２規制部材７０Ｂが、第２連結部材６１と異なる周方向位置に配設されたボルトＢ２により固定されている。具体的には、図４に示すように、第２規制部材７０Ｂは、第２規制部材７０Ｂのボス７０Ｂａに挿通され、外側部材６７の内周側端部６７ａに螺合したボルトＢ２によって外側部材６７に固定されている。この第２規制部材７０Ｂによって図２に示した第２連結部材６１の前面が覆われている。内側部材６９は外側部材６７に対して軸方向にも移動可能であり、その軸方向位置は第２規制部材７０Ｂと外側部材６７の外周側端部６７ａとにより規制されている。 An annular second restricting member 70B is fixed to the front surface of the inner peripheral end 67a of the outer member 67 shown in FIG. 2 by a bolt B2 disposed at a circumferential position different from that of the second connecting member 61. Yes. Specifically, as shown in FIG. 4, the second restricting member 70B is inserted into the boss 70Ba of the second restricting member 70B and is screwed into the inner peripheral side end 67a of the outer member 67 by the bolt B2. 67 is fixed. The front surface of the second connecting member 61 shown in FIG. 2 is covered with the second restricting member 70B. The inner member 69 is also movable in the axial direction with respect to the outer member 67, and the axial position thereof is restricted by the second restricting member 70 </ b> B and the outer peripheral end 67 a of the outer member 67.
　第３連結部材６３は、その頭部６３ｃ寄りの基端部に設けられたねじ部６３ｂを有するねじ付きピンとして形成されている。外側部材６７の外周側端部６７ｂは、径方向外側に開口する環状の連結凹部を有しており、その前壁６７ｂａに第３連結部材６３のねじ部６３ｂが螺合し、後壁６７ｂｂに設けられた嵌合穴６７ｄに第３連結部材６３の先端側のピン部６３ａの先端部が嵌合している。図３（ｂ）に示すように、タービンノズル２５の連結フランジ部２５ａには、内側部材６９の内周側の係合部６９ｂａと同様の構造を有する係合部２５ａａが設けられており、タービンノズル２５の係合部２５ａａが第３連結部材６３のピン部６３ａに係合することにより、外側部材６７がタービンノズル２５に対して周方向に相対移動不能に、且つ径方向に相対移動可能に連結されている。 The third connecting member 63 is formed as a threaded pin having a threaded portion 63b provided at the proximal end near the head 63c. The outer peripheral side end 67b of the outer member 67 has an annular connecting recess that opens radially outward. The threaded portion 63b of the third connecting member 63 is screwed into the front wall 67ba, and the rear wall 67bb is engaged. The distal end portion of the pin portion 63a on the distal end side of the third connecting member 63 is fitted in the provided fitting hole 67d. As shown in FIG. 3B, the coupling flange portion 25a of the turbine nozzle 25 is provided with an engagement portion 25aa having the same structure as the engagement portion 69ba on the inner peripheral side of the inner member 69. When the engaging portion 25aa of the nozzle 25 engages with the pin portion 63a of the third connecting member 63, the outer member 67 cannot move relative to the turbine nozzle 25 in the circumferential direction and can move relative to the radial direction. It is connected.
　なお、連結部材５９，６１，６３及び係合部６９ａａ，６９ｂａ，２５ａａはそれぞれ、周方向に３箇所以上等間隔に設けられている。また、図２に示すように、ガスタービンエンジン１の組立時において、外側部材６７の外周側端部６７ｂと、タービンノズル２５の連結フランジ部２５ａの基部２５ｂとの間には、アダプタリング５７の径方向の膨張を吸収するための隙間７１が設けられている。また、タービンノズル２５の連結フランジ部２５ａには、外側部材６７との間をシールするシール部材７３が設けられている。 The connecting members 59, 61, 63 and the engaging portions 69aa, 69ba, 25aa are provided at equal intervals in three or more locations in the circumferential direction. Further, as shown in FIG. 2, when the gas turbine engine 1 is assembled, the adapter ring 57 is interposed between the outer peripheral end 67 b of the outer member 67 and the base 25 b of the connecting flange 25 a of the turbine nozzle 25. A gap 71 for absorbing radial expansion is provided. Further, a sealing member 73 that seals between the outer flange 67 and the outer member 67 is provided on the connecting flange portion 25 a of the turbine nozzle 25.
　　以下、アダプタリング５７及び第１段のタービン動翼３１の周辺のシール構造を詳しく説明する。図２に示すように、タービン動翼３１は、高圧タービンロータ１１Ｂを形成するロータディスク７５の外周部に形成されている。アダプタリング５７の内側部材６９の内部には、圧縮空気移送空間５５から、内側部材６９とロータディスク７５の間の内径側空間７７に、圧縮空気１２０の一部を冷却空気１２５として導出する予旋回ノズル７９が設けられている。ロータディスク７５の、予旋回ノズル７９に対向する部分には、冷却空気１２５をロータディスク７５内部へ導入する冷却通路８１が設けられている。したがって、圧縮空気移送空間５５から内径側空間７７に導出された冷却空気１２５は、ロータディスク７５の外部および内部を冷却する。一方、アダプタリング５７の外側部材６７とロータディスク７５との間に形成される外径側空間８３には、回転部材である第１段のタービン動翼３１と非回転部材であるタービンノズル２５との隙間３３から、タービン７の燃焼ガス通路８４を通る高温の燃焼ガスＧの一部が漏れガス２６０として流入する。 Hereinafter, the seal structure around the adapter ring 57 and the first stage turbine blade 31 will be described in detail. As shown in FIG. 2, the turbine rotor blade 31 is formed on the outer peripheral portion of the rotor disk 75 that forms the high-pressure turbine rotor 11B. In the inside of the inner member 69 of the adapter ring 57, a pre-swirl for extracting a part of the compressed air 120 as cooling air 125 from the compressed air transfer space 55 to the inner diameter side space 77 between the inner member 69 and the rotor disk 75. A nozzle 79 is provided. A cooling passage 81 for introducing the cooling air 125 into the rotor disk 75 is provided in a portion of the rotor disk 75 facing the pre-swivel nozzle 79. Therefore, the cooling air 125 led out from the compressed air transfer space 55 to the inner diameter side space 77 cools the outside and the inside of the rotor disk 75. On the other hand, in the outer diameter side space 83 formed between the outer member 67 of the adapter ring 57 and the rotor disk 75, the first stage turbine rotor blade 31 as a rotating member and the turbine nozzle 25 as a non-rotating member are provided. A part of the high-temperature combustion gas G passing through the combustion gas passage 84 of the turbine 7 flows in as leak gas 260 from the gap 33.
　アダプタリング５７の外側部材６７と内側部材６９との連結部分の後側には、前方に凹む環状の凹部８５が設けられている。一方、ロータディスク７５の前側の、凹部８５に対応する径方向位置には、高圧タービンロータ１１Ｂの軸方向に突出し、且つ周方向に延びる環状の突起部８７が設けられており、この突起部８７には、径方向外側と内側とにそれぞれ複数のラビリンス歯８９が形成されている。これにより、突起部８７と外側部材６７との間をシールする外側ラビリンスシール９１と、突起部８７と内側部材６９との間をシールする内側ラビリンスシール９３とを有する二重のラビリンスシール機構であるシール構造が形成される。このシール構造により、高温の漏れガス２６０が流入する外径側空間８３と、冷却空気１２５が流入する内径側空間７７との間がシールされる。その結果、外径側空間８３内の漏れガス２６０が内径側空間７７に侵入して冷却作用が低下することを防止できる。 An annular recess 85 that is recessed forward is provided on the rear side of the connecting portion between the outer member 67 and the inner member 69 of the adapter ring 57. On the other hand, an annular protrusion 87 that protrudes in the axial direction of the high-pressure turbine rotor 11 </ b> B and extends in the circumferential direction is provided at a radial position corresponding to the recess 85 on the front side of the rotor disk 75. A plurality of labyrinth teeth 89 are respectively formed on the radially outer side and the inner side. This is a double labyrinth seal mechanism having an outer labyrinth seal 91 that seals between the protrusion 87 and the outer member 67 and an inner labyrinth seal 93 that seals between the protrusion 87 and the inner member 69. A seal structure is formed. With this sealing structure, the space between the outer diameter side space 83 into which the high-temperature leaking gas 260 flows and the inner diameter side space 77 into which the cooling air 125 flows is sealed. As a result, it is possible to prevent the leakage gas 260 in the outer diameter side space 83 from entering the inner diameter side space 77 and reducing the cooling action.
　なお、外側部材６７及び内側部材６９における突起部８７のラビリンス歯８９に対向する部分には、それぞれ、ニッケル－鉄合金からなるハニカム構造のアブレイダブル材９５が固定されている。これにより、ラビリンスシール機構であるシール構造ＳＳを形成する突起部８７と外側部材６７、内側部材６９との摩耗が抑制され、シール構造の寿命が向上する。 It should be noted that an abradable material 95 having a honeycomb structure made of a nickel-iron alloy is fixed to portions of the outer member 67 and the inner member 69 facing the labyrinth teeth 89 of the protrusion 87. As a result, the wear of the protrusion 87, the outer member 67, and the inner member 69 forming the seal structure SS, which is a labyrinth seal mechanism, is suppressed, and the life of the seal structure is improved.
　アダプタリング５７の内側部材６９は、外側部材６７よりも熱膨張率の大きな材料により形成されている。内側部材６９と外側部材６７の熱膨張率の差は、２×１０－６～６×１０－６／℃の範囲にあることが好ましく、３×１０－６～５×１０－６／℃の範囲にあることがより好ましい。本実施形態では、内側部材６９を形成する材料としてＳＵＳ３２１のようなステンレス鋼を用い、外側部材６７を形成する材料としてＷＡＳＰＡＬＯＹ（登録商標）のようなＮｉ系耐熱合金を使用している。ＳＵＳ３２１の熱膨張率は、約１８×１０－６／℃、ＷＡＳＰＡＬＯＹの熱膨張率は、約１４×１０－６／℃であり、両者の差は、約４×１０－６／℃である。 The inner member 69 of the adapter ring 57 is made of a material having a larger coefficient of thermal expansion than the outer member 67. The difference in coefficient of thermal expansion between the inner member 69 and the outer member 67 is preferably in the range of 2 × 10 −6 to 6 × 10 −6 / ° C., and is 3 × 10 −6 to 5 × 10 −6 / ° C. More preferably, it is in the range. In this embodiment, stainless steel such as SUS321 is used as a material for forming the inner member 69, and a Ni-based heat-resistant alloy such as WASPALOY (registered trademark) is used as a material for forming the outer member 67. The thermal expansion coefficient of SUS321 is about 18 × 10 −6 / ° C., and the thermal expansion coefficient of WASPALOY is about 14 × 10 −6 / ° C., and the difference between the two is about 4 × 10 −6 / ° C.
　本実施形態に係るタービンロータのシール構造によれば、アダプタリング５７の内側部材６９は、外側部材６７よりも熱膨張率の大きな材料で形成されているので、シール構造のシール性が向上する。すなわち、ガスタービンエンジン１の運転時、熱膨張及び遠心力によりタービンロータ（高圧タービンロータ１１Ｂ）が径方向外側に膨張することに伴い、突起部８７が径方向外側に変位するが、外側部材６７は熱膨張による径方向外側への変位量が少ない。したがって、突起部８７の径方向外側部分と熱膨張率の小さい外側部材６７とによって、シール構造の外側ラビリンスシール９１のシール性が確保される。他方、熱膨張率の大きい内側部材６９は、熱膨張によって径方向外側へ大きく変位することにより、突起部８７の変位に追随するので、シール構造の内側ラビリンスシール９３のシール性が大幅に向上する。このように、シール構造全体の軸方向寸法の増大をともなうことなく、シール構造のシール性を向上できる。 According to the seal structure of the turbine rotor according to the present embodiment, the inner member 69 of the adapter ring 57 is formed of a material having a larger coefficient of thermal expansion than the outer member 67, so that the sealing performance of the seal structure is improved. That is, when the gas turbine engine 1 is operated, the protrusion 87 is displaced radially outward as the turbine rotor (high-pressure turbine rotor 11B) expands radially outward due to thermal expansion and centrifugal force. Is less displaced radially outward due to thermal expansion. Therefore, the sealing performance of the outer labyrinth seal 91 having a sealing structure is ensured by the radially outer portion of the protrusion 87 and the outer member 67 having a low coefficient of thermal expansion. On the other hand, the inner member 69 having a large coefficient of thermal expansion largely displaces radially outward due to thermal expansion, thereby following the displacement of the protrusion 87, so that the sealing performance of the inner labyrinth seal 93 of the seal structure is greatly improved. . Thus, the sealing performance of the seal structure can be improved without increasing the axial dimension of the entire seal structure.
　例えば、本実施の形態では、突起部８７の径方向外側と内側とにラビリンス歯８９をそれぞれ４つずつ設けているので、ラビリンス歯８９を径方向外側のみに４つ設けた場合と同等の軸方向寸法を維持しながら、ラビリンス歯８９を径方向外側のみに８つ設けた場合と同等のシール性を有している。なお、突起部８７の径方向外側及び内側に設けるラビリンス歯８９の数は、適宜に選択できる。 For example, in the present embodiment, four labyrinth teeth 89 are provided on each of the radially outer side and the inner side of the protrusion 87, and therefore, the same axis as when four labyrinth teeth 89 are provided only on the radially outer side. While maintaining the directional dimension, the sealing performance is equivalent to the case where eight labyrinth teeth 89 are provided only on the radially outer side. The number of labyrinth teeth 89 provided on the radially outer side and the inner side of the protrusion 87 can be selected as appropriate.
　今回、開示した実施の形態は例示であってこれに制限されるものではない。本発明は、上記で説明した範囲ではなく、特許請求の範囲によって示され、特許請求の範囲と均等の意味及び範囲での全ての変更を含む。 The embodiment disclosed this time is an example, and the present invention is not limited to this. The present invention is defined by the scope of the claims rather than the scope described above, and includes all modifications within the scope and meaning equivalent to the scope of the claims.

Claims (4)

  1. 　ガスタービンエンジンにおけるタービンロータのシール構造であって、
    　前記タービンロータに設けられた突起部と、この突起部の径方向外側に配置され、径方向に変位可能に支持された外側部材と、前記突起部の径方向内側に配置され、径方向に変位可能に支持された内側部材とで形成されるラビリンスシールを含み、
    　前記内側部材の熱膨張率が、前記外側部材の熱膨張率よりも大きく設定されていることを特徴とするタービンロータのシール構造。     A seal structure of a turbine rotor in a gas turbine engine,
    A protrusion provided on the turbine rotor, an outer member disposed radially outside the protrusion, and supported so as to be radially displaceable, and disposed radially inside the protrusion, and displaced in the radial direction. A labyrinth seal formed with an inner member supported in a possible manner,
    The seal structure of a turbine rotor, wherein a thermal expansion coefficient of the inner member is set larger than a thermal expansion coefficient of the outer member.
  2. 　前記内側部材の熱膨張率と前記外側部材の熱膨張率との差が、２×１０－６～６×１０－６／℃の範囲内にあることを特徴とする請求項１に記載のタービンロータのシール構造。 2. The turbine according to claim 1, wherein a difference between a coefficient of thermal expansion of the inner member and a coefficient of thermal expansion of the outer member is in a range of 2 × 10 −6 to 6 × 10 −6 / ° C. Rotor seal structure.
  3. 　前記外側部材における前記突起部と対向する部分に、アブレイダブル材が設けられていることを特徴とする請求項１又は請求項２に記載のタービンロータのシール構造。 The turbine rotor seal structure according to claim 1 or 2, wherein an abradable material is provided at a portion of the outer member facing the protrusion.
  4. 　前記内側部材における前記突起部と対向する部分に、アブレイダブル材が設けられていることを特徴とする請求項１から請求項３のいずれか１項に記載のタービンロータのシール構造。 The turbine rotor seal structure according to any one of claims 1 to 3, wherein an abradable material is provided at a portion of the inner member facing the protrusion.
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EP2551492A4 (en) 2016-12-14
US20130200571A1 (en) 2013-08-08
US9359958B2 (en) 2016-06-07
CA2793966C (en) 2015-04-07
CA2793966A1 (en) 2011-09-29
EP2551492A1 (en) 2013-01-30
EP2551492B1 (en) 2020-02-26
JP2011196356A (en) 2011-10-06
JP4856257B2 (en) 2012-01-18

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